Rolls-royce North American Technologies Inc.

Stephen A Bergeron

Bryan H Lerg

Robert Anthony Ress, Jr

Emil R Dejulio

Randall E Yount

Victor Oechsle

Christopher J Bies

Benjamin R Harding

A nozzle is provided that is capable providing flowpaths for a combined cycle aircraft propulsion system that in one form includes a gas turbine engine and a ramjet. The gas turbine engine produces an exhaust flow that is offset from an exhaust flow from the ramjet. The two streams can be flowed independent of each other or together depending on the application and relevant portion of a flight envelope. The nozzle includes a movable portion that can selectively open and close an exhaust flowpath for the gas turbine engine. The nozzle includes a surface that provides expansion for both low speed (gas turbine engine) flow and high speed (ramjet) flow.

Aircraft nozzle system

A gas turbine engine having a ramburner is disclosed. The ramburner is disposed downstream of a gas turbine engine combustor and receives an engine exhaust flow from the gas turbine engine combustor. The ramburner also accepts a bypass air. Fuel is injected into the ramburner and a combustion reaction is auto-initiated based upon local gas temperatures. No mechanical flame holders need be used. A slidable valve may be used to vary the amount of bypass air into the ramburner. A movable cowl and a plug nozzle form an exit flow path of the gas turbine engine. The movable cowl can be positioned to vary a throat area and exit area of the gas turbine engine based upon the operation of the ramburner, which may be influenced by the amount of bypass air entering the ramburner.

Combustor added to a gas turbine engine to increase thrust

An exhaust device is disclosed that includes a duct that turns an exhaust flow from a gas turbine engine from a first direction to a second direction. A diverter cup is disposed within the duct and serves to split the exhaust flow into two streams as well as introduce cooling air through an ejector pump at the downstream end of the diverter cup. A splitter is disposed downstream of the diverter cup and serves to split the cooling air into two streams which are thereafter mixed with the split exhaust flow. A diffuser is created in the exhaust device between the duct and the splitter. Various cooling slots are also provided in the duct.

Gas turbine exhaust assembly

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Indianapolis, IN, United States of America

Stephen A Bergeron